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naca-6214

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Generated NACA airfoil. See also http://www.aerospaceweb.org/question/airfoils/q0041.shtml

Thickness:	14.0%
Camber:	6.0%
Trailing edge angle:	16.7^o
Lower flatness:	94.5%
Leading edge radius:	2.2%

Max C_L:	1.797
Max C_L angle:	15.0
Max L/D:	45.945
Max L/D angle:	1.5
Max L/D C_L:	0.879
Stall angle:	2.5
Zero-lift angle:	-5.5